Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine

Mota, Fábio Antônio da Silva; Hinckel, José Nivaldo; Rocco, Evandro Marconi; Schlingloff, Hanfried

doi:10.5028/jatm.v10.914

Fábio Antônio da Silva Mota Correspondence author: Fábio Antônio da Silva Mota | Universidade Federal do ABC - Centro de Engenharia, Modelagem e Ciências Sociais Aplicadas - Departamento de Engenharia Aeroespacial | Av. dos Estados, 5001 | CEP: 09.210-580 - Santo André/SP - Brazil | E-mail: mota.fabio@ufabc.edu.br

Universidade Federal do ABC - Centro de Engenharia, Modelagem e Ciências Sociais Aplicadas - Departamento de Engenharia Aeroespacial - Santo André/SP - Brazil

http://orcid.org/0000-0003-3672-0547

José Nivaldo Hinckel

Instituto Nacional de Pesquisas Espacias - Departamento de Engenharia e Tecnologia Espacial - São José dos Campos/SP - Brazil

http://orcid.org/0000-0002-0171-2697

Evandro Marconi Rocco

Instituto Nacional de Pesquisas Espacias - Departamento de Engenharia e Tecnologia Espacial - São José dos Campos/SP - Brazil

http://orcid.org/0000-0003-0660-0587

Hanfried Schlingloff

Ostbayerische Technische Hochschule Regensburg - Department of Mechanical Engineering - Regensburg - Germany.

http://orcid.org/0000-0003-1806-9113

Correspondence author: Fábio Antônio da Silva Mota | Universidade Federal do ABC - Centro de Engenharia, Modelagem e Ciências Sociais Aplicadas - Departamento de Engenharia Aeroespacial | Av. dos Estados, 5001 | CEP: 09.210-580 - Santo André/SP - Brazil | E-mail: mota.fabio@ufabc.edu.br

Section Editor: Carlos Marchi

AUTHOR'S CONTRIBUTION

Conceptualization, Mota FAS, Hinckel JN and Rocco EM; Methodology, Mota FAS, Hinckel JN and Schlingloff H; Writing - Original Draft, Mota FAS; Writing - Review & Editing, Mota FAS, Hinckel JN, Rocco EM and Schlingloff H.

LRE	Propellant	Actual (kg) (Mc Hugh 1995Mc Hugh B (1995) Numerical analysis of existing liquid rocket engines as a design process starter. Presented at: 31st Joint Propulsion Conference and Exhibit; San Diego, USA. doi: 10.2514/6.1995-2970 https://doi.org/10.2514/6.1995-2970... )	Calculated (kg)	Error
HM7B	LOX/LH2	158.0	167.2	5.8
HM60	LOX/LH2	1719.0	1809.2	5.2
LE-5	LOX/LH2	255.0	324.2	27.1
J-2	LOX/LH2	1542.0	1440.4	6.6
H-1	LOX/RP-1	878.2	932.2	6.2
RS-27	LOX/RP-1	1146.6	1060.7	7.5

Vulcain	Actual (Pouliquen 1984Pouliquen MF (1984) HM60 cryogenic rocket engine for future European launchers. Journal of Spacecraft and Rockets 21(4):346-353. doi: 10.2514/3.25661 https://doi.org/10.2514/3.25661... ; Mc Hugh 1995Mc Hugh B (1995) Numerical analysis of existing liquid rocket engines as a design process starter. Presented at: 31st Joint Propulsion Conference and Exhibit; San Diego, USA. doi: 10.2514/6.1995-2970 https://doi.org/10.2514/6.1995-2970... )	Calculated	Error (%)
Key input
F (kN)	1025	-	-
p_c(bar)	100	-	-
r_c	5.9	-	-
A_e / A_t	45	-	-
Output
I_sp(s)	433.5	433.291	0.05
ṁ_g (kg/s)	8.4	8.625	2.68
ṁ_T_,_o (kg/s)	-	3.234	-
	-	5.391	-
ṁ_o_,_c (kg/s)	198.0	206.267	4.17
ṁ_f_,_c (kg/s)	34.0	35.420	4.18
P_T_,_o (MW)	3.0	3.13	4.33
P_T_,_f (MW)	11.2	12.054	7.63

HM7B	Actual (Mc Hugh 1995Mc Hugh B (1995) Numerical analysis of existing liquid rocket engines as a design process starter. Presented at: 31st Joint Propulsion Conference and Exhibit; San Diego, USA. doi: 10.2514/6.1995-2970 https://doi.org/10.2514/6.1995-2970... )	Calculated	Error (%)
Key input
F (kN)	62.2	-	-
p_c(bar)	36	-	-
r_c	5.15	-	-
A_e / A_t	82.9	-	-
Output
I_sp(s)	445.5	451.03	1.24
p_d_,_o (bar)	50.2	50	0.40
p_d_,_f (bar)	55.5	55.3	0.36
ṁ_g (kg/s)	0.25	0.237	5.2
ṁ_T (kg/s)	0.25	0.237	5.2
ṁ_c (kg/s)	13.9	14.045	1.04
P_T(kW)	404	397.2	1.68

SSME	Manski and Martin (1991)Manski D, Martin JA (1991) Evaluation of innovative rocket engines for single-stage Earth-to-orbit vehicles. Journal of Propulsion and Power 7(6):929-937. doi: 10.2514/3.23411 https://doi.org/10.2514/3.23411...	Calculated	Error (%)
Key input
F (kN)	2273	-	-
p_c(bar)	219.70	-	-
r_c	6.019	-	-
A_e / A_t	77.5	-	-
Output
I_sp(s)	444.0	451.267	1.63
ṁ_o_,_pb₁(kg/s)	36.90	42.723	15.8
ṁ_f_,_pb₁ (kg/s)	37.81	43.774	15.8
ṁ_o_,_pb₂ (kg/s)	13.56	13.941	2.81
ṁ_f_,_pb₂ (kg/s)	19.94	20.501	2.81
ṁ_{T, LPOTP} (kg/s)	83.06	82.89	0.20
ṁ_c (kg/s)	511.46	514.814	0.66
P_T_,_HPFTP (MW)	57.79	66.87	15.7
P_T_,_HPOTP (MW)	21.77	22.38	2.8

L75 Rocket Engine
pc (bar) (given)	30	40	50	58.5	80	100
Isp(vac) (s) (calculated)	315.067	315.89	315.93	315.61	313.83	311.45
Ae / At (-) (calculated)	87.828	109.56	130.16	147	187.51	223.22

\begin{matrix} f_{1} (x_{1}, x_{2}, \dots, x_{N}) = 0 \\ f_{2} (x_{1}, x_{2}, \dots, x_{N}) = 0 \\ ⋮ \\ f_{N} (x_{1}, x_{2}, \dots, x_{N}) = 0 \end{matrix}

[1] Correspondence author: Fábio Antônio da Silva Mota | Universidade Federal do ABC - Centro de Engenharia, Modelagem e Ciências Sociais Aplicadas - Departamento de Engenharia Aeroespacial | Av. dos Estados, 5001 | CEP: 09.210-580 - Santo André/SP - Brazil | E-mail: mota.fabio@ufabc.edu.br

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Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine

ABSTRACT